DR2 Aerodynamic PDR II Aerodynamic Preliminary Design Review II “The 20 Hour Marathon” October 19, 2000 Presented By: Loren Garrison Team DR2 Chris Curtis Chris Peters Jeff Rodrian Mark Blanton

DR2 Aerodynamics PDR II Presentation Outline Updated Aircraft Geometry Comparison of 3-D Lift and Drag Coefficients 3-D Lift, Drag, and Moment Coefficients with elevator deflection effects Maximum Endurance Flight Conditions Cmarc Developments

DR2 Aerodynamics PDR II Wing Geometry - Airfoil:S Taper Ratio:1.0 - Dihedral Angle:0 (deg) - Sweep Angle:0 (deg) - Aspect Ratio:8 - Span:7.71 (ft) - Root Chord:0.96 (ft) - Tip Chord:0.96 (ft) - Planform Area:14.9 (ft 2 ) - Wetted Area:29.7 (ft 2 )

DR2 Aerodynamics PDR II Horizontal Tail Geometry - Airfoil:NACA Taper Ratio: Dihedral Angle:0 (deg) - Sweep Angle:4.0 (deg) - Aspect Ratio:4 - Span:2.88 (ft) - Root Chord:0.82 (ft) - Tip Chord:0.62 (ft) - Planform Area:2.07 (ft 2 ) - Wetted Area:4.22 (ft 2 )

DR2 Aerodynamics PDR II Vertical Tail Geometry - Airfoil:NACA Taper Ratio:0.6 - Dihedral Angle:0 (deg) - Sweep Angle:5.60 (deg) - Aspect Ratio:2.5 - Span:1.81 (ft) - Root Chord:0.91 (ft) - Tip Chord:0.54 (ft) - Planform Area:1.31 (ft 2 ) - Wetted Area:2.68 (ft 2 )

DR2 Aerodynamic PDR II

DR2 Aerodynamics PDR II 3-D Lift Curve (Roskam Method)

DR2 Aerodynamics PDR II 3-D Lift Curve (Roskam Method)

DR2 Aerodynamics PDR II 3-D Lift Curve (Roskam Method)

DR2 Aerodynamics PDR II 3-D Lift Curve Slope (Warner Method),where n=1+  for b u =b l

DR2 Aerodynamics PDR II 3-D Lift Curve (Warner Method)  and  are determined from a curve fit to the data in Warner, Aircraft Design: Performance

DR2 Aerodynamics PDR II 3-D Drag Polar (Roskam) (Warner)

DR2 Aerodynamics PDR II 3-D Lift Curve for the Aircraft using the Roskam and Warner Methods

DR2 Aerodynamics PDR II 3-D Drag Polar for the Aircraft using the Roskam and Warner Methods

DR2 Aerodynamics PDR II 3-D L/D for the Aircraft using the Roskam and Warner Methods

DR2 Aerodynamics PDR II 3-D Endurance Parameter for the Aircraft using the Roskam and Warner Methods

DR2 Aerodynamics PDR II 3-D Lift Curve with Elevator Deflections 3-D Lift Curve Slope (Warner Method),where n=1+ 

DR2 Aerodynamics PDR II 3-D Lift Curve Slope (Warner Method)  and  are determined from a curve fit to the data in Warner, Aircraft Design: Performance

DR2 Aerodynamics PDR II 3-D Lift Curve with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Moment Coefficient with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Moment Coefficient with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Drag Polar with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Coefficient Summary C Lo = C L   = rad -1 C L  e = rad -1 C mo = C m  = rad -1 C m  e = rad -1 C Do =

DR2 Aerodynamics PDR II 3-D Lift Curve with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Moment Coefficient with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Drag Polar with Elevator Deflections

DR2 Aerodynamics PDR II 3-D L/D with Elevator Deflections

DR2 Aerodynamics PDR II 3-D Maximum L/D

DR2 Aerodynamics PDR II 3-D Endurance Parameter

DR2 Aerodynamics PDR II Flight Conditions for Maximum Endurance V loiter = 23.9 ft/s Angle of Attack = 6.61 deg CL = 0.91 CD = Maximum L/D L/D max = 15.0

DR2 Aerodynamics PDR II

DR2 Aerodynamics PDR II Future Tasks Extract CL and CD values from the Cmarc model to compare to the theory Run the Cmarc stability test to determine the aerodynamic derivatives and compare to the theory Evaluate the Trim ability, Stability, and Controllability considerations